摘要
利用计算流体动力学方法建立了发射箱内燃气流场计算分析模型,对火箭弹发射时箱内压力波传播进行了数值分析,获得了箱内前后出口处的流场压力。通过合理的设计开盖压力,能可靠实现发射箱前后盖的自动开启。经飞行试验验证,数值分析结果与试验情况吻合良好,表明箱内燃气流场计算分析模型的正确性。
The numerical model of gas flow spread on launcher box was built by using CFD methods and the flow pressures at pre-cover and post-cover of launcher were obtained. Through rational designs pre-cover and post-cover opening pressure, pressure wave is big enough to automatically open launcher cover. By flight experimental verification, numerical analysis and experiments are in good agreement, indicates the gas flow model on launcher is correct and reasonable.
出处
《强度与环境》
2014年第5期24-27,共4页
Structure & Environment Engineering
基金
国防科技工业军贸科研项目
关键词
发射箱
压力波
数值分析
试验
launcher pressure wave numerical analysis experiment
